INSTALLATION OF HIGH-PRESSURE TURBINE NOZZLE IN LEAKAGE-PROOF MODE AT ONE END OF COMBUSTION CHAMBER IN GAS TURBINE

摘要

PROBLEM TO BE SOLVED: To achieve the optimized installation of a high-pressure turbine nozzle at the end part of a combustion chamber. SOLUTION: The downstream side end part portions 12a and 13a of the inner and outer wall parts 12 and 13 of the combustion chamber 10 of a gas turbine are pressed against the inner and outer platforms 22 and 23 of the vane 21 of the high-pressure turbine nozzle 20, and substantially extend to the upper part of the downstream side ends of the platforms. A means for mechanically connecting the turbine nozzle 20 to the downstream side end part portions 12a and 13a of a combustion chamber wall part is formed of connection screws 25 and 27 fitted into the airfoil 21 of the vane of the turbine nozzle passing a hole part formed at the end part portion of the combustion chamber wall part. As a result, the downstream side end part portion of the combustion chamber wall part contributes to prevent leakage from a gas flow in a boundary surface between the combustion chamber and the nozzle and along the nozzle. COPYRIGHT: (C)2006,JPO&NCIPI